Single/multiple guard(s)/cap(s) and/or screen(s) with engine attached apparatus and/or pole with rotational system(s)-centrifuge chamber/manifold particle collector

ABSTRACT

This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is based upon and claims the priority of U.S.Provisional Patent Application Ser. No. 60/167,163, filed on Nov. 23,1999.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to a system for preventing and/orseparation foreign objects from the air intake of a turbine engine. Inparticular, this invention relates in general to a single/multipleguard(s)/cap(s) and/or screen(s) with engine shaft apparatus and/orpole. Extensions/rods can be laced, for example, fixed/secured, adhered,positioned and/or attached to the guard(s)/cap(s) and/or screen(s); aswell as to the engine shaft extension(s) and/or pole apparatus, and/orrotational systems. The rotational system(s)—functions with complete,pivot and/or partial movement (for example) for gas separation, for thenacelle/air inlet of numerous jet engines, turbojet, turboprop andturboshaft engines such as aircraft and power plants or the like. Theaddition of the centrifuge chamber/manifold particle collector withrotational system(s) would further add security means without limitingengine thrust.

2. Description of the Prior Art

Problems are caused by ingestion of foreign objects into the nacelle/airinlet of engines; this problem has been previously known and recognized,for example, as disclosed in U.S. Pat. Nos. 2,695,074; 2,931,460;2,944,631; 2,969,941; 3,121,545; 3,148,043; 3,426,981; 3,521,431;3,616,616; 3,766,719; 3,832,086; 3,871,844; 4,149,689; 4,265,646;4,617,028; 4,833,879; 5,046,458 and 5,411,224, all hereby incorporatedby reference. However, such systems are known to limit engine thrustthus solving one problem and creating another. Since jet engines,turbojet, turboprop and/or turboshaft aircraft operate in environmentswhere foreign objects cannot be controlled or removed solutions must befound in order to solve this problem. Numerous aircraft have reportedsuch problems with foreign objects, yet constructive solutions have notbeen previously found. Such problems with ingestion of foreign objectsto engines causes damage in the compressor stage and to other portionsof the engine. Such engine damage is immediate by partial or completeengine thrust surmounting to impairment of aircraft's flying ability.Since many of the systems used in aircraft are limited in function ofengine capability, for example, two engines, such limitation can bedetrimental and/or fatal. The possible injestion of foreign objects inengines during or shortly after aircraft take-off (ascending) and oraircraft landing (descent) can be grave consequence.

The advent of gas turbine helicopters and other vehicles take-off andlanding with VTOL/VSTOL aircraft, foreign matter—particles are also ofgrave concert. Helicopters and other VTOL/VSTOL aircraft are alsoespecially suited for certain low altitude missions on both land andsea, including combat support, search and rescue, and anti-submarinewarfare; this foreign particle matter leaves the aircraft in a gravesituation. Therefore, it is desirable to provide means as a guard and aparticle collector for such conditions to ensure safety.

SUMMARY OF THE INVENTION

This invention relates in general to a guard(s)/cap(s) and/or screen(s)apparatus (single and/or multiple formation—along with themanipulations) for the nacelle/air inlet for numerous jet engines,turbojet, turboprop, turboshaft engines—(Helicopters and VTOL/VSTOLaircraft) such as aircraft power plants or the like. The guard(s)/cap(s)and/or screen(s) minimize if not eliminate entry of foreign objects intothe nacelle/air inlet thereby allowing the function of the aircraft tooperate respectively. In order for the appropriate unction to occur gasseparation must take place. In accordance with an important aspect ofthe invention, system(s) may be implemented with or withouttreads/threads (for example)—(along with the manipulations) that wouldallow the guard(s)/cap(s) and/or screen(s) to function accordingly forgas separation. The rotational system(s) and the guard(s)/cap(s) and/orscreen(s), shall function with the invention of the engine shaftextension(s) attachment and/or pole apparatus (along with themanipulations). The invention of the extensions/rods from theguard(s)/cap(s) and/or screen(s) shall be fixed/secured, adhered,positioned and/or attached to the rotational system(s) and/or directlyto the engine shaft extension(s) attachment and/or pole apparatus. Theengine shaft extension(s) attachment and/or pole apparatus, with theextensions/rods from the guard(s)/cap(s) and/or screen(s) shall befixed/secured, adhered and/or attached to the inward and/or outwardportion of the guard(s)/cap(s) and/or screen(s)—(along with themanipulations). Extensions/rods can also be attachedlatitudinal/longitudinal and/or laced (for example) on theguard(s)/cap(s) and/or screen(s) of the rotational system(s). Thusadhering fixed/secured and/or positioned to the rotational system(s)and/or directly to the engine shaft extension(s) attachment and/or poleapparatus. Opening and Closure of apparatus can be attained by centeraxis—for example of the guard(s)/cap(s) and/or screen(s) in multiplesections (2 and/or odd numbers). Thus closure can occur upon the engineshaft attached apparatus and/or pole in a folding or laced process (forexample) along with the extensions/rods. Therefore, allowing continuousmotion and/or function to occur from the engine without obstruction orfurther automation nor limiting engine thrust.

Additional security measures are taken with the centrifugechamber/manifold particle collector with or without ejector system(s),through conduit means. Such additional security system would ensure anydoubt of foreign particle entry and destruction prior to reaching mainengine components—compressor, combustor, a gas generator turbine fordriving the compressor and power turbine for the driving of an outputshaft. Thus, the rotational system(s) and engine-attached apparatuswould ensure continuous motion and/or function to occur from the enginewith further security system means without limiting engine thrust.

DESCRIPTION OF THE DRAWING

These and other advantages of the present invention will be readilyunderstood with reference to the following specification and attacheddrawing wherein:

FIG. 1 shows an isometric view of double guards/caps and/or screens withengine attached apparatus and/or pole, with rotational system.Additional security by means of the centrifuge chamber/manifold particlecollector-separator is with rotational system. Guard/cap and/or screenin the nacelle/air inlet according to the disclosed embodiment of thepresent invention;

FIG. 2 shows an isometric view of the double guards/caps and/or screenswith engine attached apparatus and/or pole, with rotational system.Centrifuge chamber/manifold particle collector-separator with theexhibited within the multi vane conical;

FIG. 3 shows an isometric partial expanded view of a multi vane doubleguards/caps and/or screens with engine attached apparatus and/or pole,with rotational systems. Centrifuge chamber/manifold particlecollector-separator with shown with expanded as well as multipleextensions/rods (exhibited in the inward position towards the securityapparatus);

FIG. 4 shows an isometric partial expanded view of a multi vane doubleguards/caps and/or screens with the engine attached apparatus and/orpole, with rotational systems. Centrifuge chamber/manifold particlecollector-separator with shown with expanded as well as multipleextensions/rods (exhibited in the outward position of the securityapparatus);

FIG. 5 shows a cross-sectional view of separator.

FIG. 6 shows the additional ejector system.

FIG. 7 shows the manifold sectional, engine attached apparatus and/orpole—(apparatus can be single, or attached, fixed,/secured on the engineattached apparatus and/or pole, or fixed secured on the guard(s)/cap(s)and/or screen(s). The manifold ma also include a mesh to further allowgas separation to take place.

FIG. 8 shows an isometric partial view of the double guards/caps and/orscreens with engine attached apparatus and/or pole, with rotationalsystems;

FIG. 9 shows an isometric partial expanded view of a double guards/capsand/or screen with engine attached apparatus and/or pole, withrotational systems;

FIG. 10 shows an isometric view of a retractable double guards/capsand/or screens with engine attached apparatus and/or pole, withrotational systems;

FIG. 11 shows an isometric partial expanded view of the doubleguard/caps and/or screens with engine attached apparatus and/or pole,with rotational systems; exhibits folding and/or laced pattern forretraction process;

FIG. 12 shows dispersing of a conical for retraction process; conicalmay take multiple forms.

FIG. 13 shows dispersing of a conical for retraction process, additionalconical is exhibited which thus also can take multiple forms.

FIG. 14 shows dispersing of a conical for retraction process; additionalconical may take multiple forms and vane guard thus shown in background;aperture of the vane guard shall have variance in aperture for gasseparation.

FIG. 15 shows the engine shaft extension security attachment and/orpole, diamond formation (for example)

FIG. 16 shows the engine shaft extension security attachment and/orpole, cylindrical form (for example).

FIG. 17 shows the engine shaft extension security attachment and/orpole, in rectangular form (for example).

FIG. 18 shows the multiple section engine attachment for retractionprocess of the apparatus and/or pole.

FIG. 19 shows the multiple section engine attachment for retractionprocess of the apparatus and/or pole.

FIG. 20 shows longitudinal apparatus and/or pole for numerous dualinlets, with a dual extending apparatus from the pole for inlet—powerplants and the like.

FIG. 21 shows longitudinal apparatus and/or pole for inlet—power plantsand the like.

FIG. 22 shows longitudinal apparatus and/or pole for numerous dualinlets, with a dual extending apparatus for both sides of the pole forthe inlet,—power plants and the like.

FIG. 23 rotational ring with serrated form (can also be inverted).

FIG. 24 rotational ring with jagged form (can also be inverted).

FIG. 25 rotational ring with rectangular form (can also be inverted).

FIG. 26 rotational ring with jagged interlocked form (can also beinverted).

FIG. 27 rotational ring with interlocked form (can also be inverted).

FIG. 28 rotational ring as coiled form (can also be inverted withoutring but in ring formation—for example as well as numerous coils).

FIG. 29 rotational ring as slotted form (can also be inverted on theoutside as well as internal portion of the ring—for example as well asnumerous slots).

FIG. 30 rotational ring as chain linked form (can also be invertedwithout ring but in ring formation—for example as well as numerouslinks).

FIG. 31 rotational ring shown with screen—multiple in longitudinal andlatitudinal lines/form (can also be without ring but in ringformation—for example).

FIG. 32 rotational ring shown with screen—multiple in latitudinallines/form (can also be without ring but in ring formation—for example).

FIG. 33 rotational ring shown with screen-pierced form—multiple piercing(can also be without ring but in ring formation—for example—solidmetal/material with pierced formation can also be in other forms as wellas geometric—for example).

FIG. 34 rotational ring shown with screen—multiple in longitudinallines/form (can also be without ring but in ring formation—for example).

FIG. 35 rotational ring shown with screen—multiple in longitudinal andlatitudinal lines/form (thicker/bolder form, can also be without ringbut in ring formation—for example).

FIG. 36 rotational ring shown with screen—multiple in longitudinal andlatitudinal lines/form—pierced (can also be without ring, and can be inother forms as well as geometric—for example).

FIG. 37 rotational ring shown with screen and multiple vanes (varianceraised/lowered in degrees)—screen in longitudinal and latitudinallines/form. Multiple vanes with screen (multiples of 2 and or oddnumbers). Apparatus can also be without ring but in ring formation—forexample.

FIG. 38 rotational ring shown with screen and multiple vanes (varianceraised/lowered in degrees)—screen in latitudinal lines/form. Multiplevanes with screen (multiples of 2 and/or odd numbers). Apparatus canalso be without ring but in ring formation—for example.

FIG. 39 rotational ring shown with screen-pierced form and multiplevanes (variance raised/lowered in degrees)—multiple piercing. Multiplevanes with screen (multiples of 2 and/or odd numbers). Apparatus canalso be without ring but in ring formation (solid metal/material withpierced formation, can also be in other forms as well as geometric—forexample). FIG. 46 a-46 d shown as internal mesh for the piercedmechanism; this can also be used for numerous functions in accordance tothe mechanism.

FIG. 40 rotational ring shown with screen and multiple vanes (varianceraised/lowered in degrees) screen longitudinal lines/form. Multiplevanes with screen (multiples of 2 and/or odd numbers). Apparatus canalso be without ring but in ring formation—for example.

FIG. 41 rotational ring shown with screen and multiple vanes (varianceraised/lowered in degrees)—screen in longitudinal and latitudinallines/form (thicker/bolder form). Multiple vanes with screen (multiplesof 2 and/or odd numbers). Apparatus can also be without ring but in ringformation—for example.

FIG. 42 rotational ring shown with screen and multiple vanes (varianceraised/lowered in degrees)—screen in longitudinal and latitudinallines/form-pierced (can be in other forms as well as geometric).Multiple vanes with screen (multiples of 2 and/or odd numbers).Apparatus can also be without ring but in ring formation—for example.

FIG. 43 rotational ring shown with screen—screen consists of multiplevanes (variance raised/lowered in degrees), with or withouttreads/threads—for example.

FIG. 44 rotational ring shown with screen—screen in longitudinal andlatitudinal lines/form pierced (can be in other forms as well asgeometric).

FIG. 45 rotational ring shown in cube form with height, width, anddepth—multiple cubes (can also be without ring but in ring formation—forexample—solid metal/material with or without cubes consisting a mesh, inmultiples of 2 and/or odd numbers. Note: cube can take other geometricforms.

FIG. 46 a, 46 b, 46 c, and 46 d consists in variance in meshing:

-   -   (a) is latitudinal, variance in degrees of aperture.    -   (b) is latitudinal and longitudinal and variance in the degrees        of aperture (dense.)    -   (c) is longitudinal, variance in degrees of aperture.    -   (d) is latitudinal and longitudinal variance in degrees of        aperture.

FIG. 47 the guard/cap shown as conical/cone, with multiple longitudinaland latitudinal lines/vanes form (rectangular-convex nose of the guard.

FIG. 48 the guard/cap shown as conical/cone, with multiple longitudinaland latitudinal lines/vanes form (convex nose of the guard with smallerscale of graduating metal/material or larger scale of metal/material).

FIG. 49 the guard/cap shown as conical/cone, with solid form (convexnose guard).

FIG. 50 the guard/cap shown as conical/cone, with multiple slits inlongitudinal lines/vanes form (convex nose guard).

FIG. 51 the guard/cap shown as conical/cone, with multiple longitudinallines/vanes form (convex nose guard).

FIG. 52 the guard/cap shown as conical/cone, pierced form—multiple inpiercing (convex nose guard can also be in other forms as well asgeometric).

FIG. 53 the guard/cap shown as conical/cone with multiple latitudinalline/vanes form (convex nose and/or guard with nose guard withcylindrical latitude form).

FIG. 53 can also be formed with latitudinal line/vanes without beingcylindrical.

FIG. 54 the guard/cap shown as conical/cone, pierced form—multiple inpiercing as well as longitudinal lines/vanes form (convex nose can alsobe in other forms—latitudinal lines may also be added for additionalobstruction.

FIG. 55 the guard/cap shown as conical/cone, with multiple longitudinallines/vanes for greater gas separation with external centrifuge manifoldparticle collector-separator.

FIG. 56 the conical with multiple external vanes (vane variance raisedand/or lowered in degrees)—solid and/or partial form (for example).

FIG. 57 the rhombus structural support frame with or without internalrotational systems, with or without treads/threads—for example, therotational system is shown in rectangular form this is one of manyconfigurations of the structural support frame.

FIG. 58 the parallelogram structural support frame with or withoutinternal rotational systems, with or without treads/threads—for example,the rotational system is shown in rectangular form this is one of manyconfigurations of the structural support frame.

FIG. 59 the spherical/round structural support frame with or withoutinternal rotational systems, with or without treads/threads—for example,the rotational system is shown in rectangular form this is one of manyconfigurations of the structural support frame.

FIG. 60, nose guard/cap shown as conical/cone form is solid formation(cone pointed).

FIG. 61, nose guard/cap shown as conical/cone form has multiplelongitudinal and latitudinal lines/vanes form (cone pointed).

FIG. 62 nose guard/cap shown as conical/cone form is solid formation(convex form).

FIG. 63 nose guard/cap shown as conical/cone form has multiplelongitudinal and latitudinal lines/vanes form (convex form).

FIG. 64 nose guard/cap shown as conical/cone form is solid formation(rectangular form).

FIG. 65 nose guard/cap shown as conical/cone form has longitudinal andlatitudinal lines/vanes form (rectangular form).

FIG. 66 nose guard/cap shown as conical/cone form is solid formation(concave form).

FIG. 67 nose guard/cap shown as conical/cone form has longitudinal andlatitudinal lines/vanes form (concave form).

DETAILED DESCRIPTION

FIG. 1 is the first embodiment exhibited in a isometric partial view ofapparatus and noted that the guards/caps and/or screens (can beinterchanged) is shown with longitudinal and latitudinal form. Thisembodiment as well as the other embodiment may consist of a dispersingeffect and/or retraction. In FIG. 1 numeral 10 a and 10 b we note thescreens, can be fixed/secured adhered, positioned and/or attached to thebases of the apparatus (can be separate apparatus), and thus fastened.The centrifuge chamber/manifold particle collector exhibited by numerals12 a and 12 b. The particle separator exhibits a pair of spacedwalls—the screens—for example—(pierced screen shown as FIG. 33—can beinternal part of the meshed screen(s) with vane(s)—for example—shown asFIG. 46 a thru 46 d) with rotational systems apparatus—exhibited bynumerals 14 a and 14 b as well as numerals 14 c and 14 d, with orwithout treads/threads—for example. Define as annular passageway therebetween, having at opposite ends thereof and outlet flow ofcommunication through two ducts exhibited by numerals 16 a and 16 blocated at opposite ends of the chamber. The vanes in the chamberexhibited by numeral 12 a and 12 b axially divide the chamber and definean annular extraction manifold. The three turning vanes each of whichextends an arcuate distance of approximately 120 degrees, (for example)it can be seen that no particle need travel more than a circumferentialdistance of 120 degrees (for example) before entering the extractionmanifold from which rebound into the engine inlet is reduced. Variancesin degrees can occur with structural configuration of guard(s)/cap(s)and/or screens(s). Number of collector vanes may vary to meet therequired amount for collector/separator efficiency. The ducts are indirect communication with the collection chambers exhibited by numerals18 a and 18 b, and thus the collection chamber is in directcommunication with the two conduits exhibited by numerals 20 a and 20 b.The chamber 18 a, 18 b may including mesh for aerodynamic purposes invarious forms as discussed herein.

As air numeral 22, passes through the inlet which is at a high velocityit is turned or centrifuged circumferentially at such a downstream ofthe vanes, the air has both angular and axial velocity. This is known asimparting “swirl” to the fluid stream. Small particles of foreign matterentrained in the air stream are also centrifuged, having small mass theparticles are carried along with the swirling air. The particles withgreater mass are not of our concern due to the guard(s)/cap(s) and/orscreen(s) are used for preventive measure. A particle entrained in theair stream and centrifuged will have both tangential and axial velocitydownstream of the turning vanes. Both tangential and axial velocity intheory not subjected to external forces travel in a straight line pathto the outer periphery of the passage way. In practice, the swirling airhas significant effect on the particles trajectory which can be comparedroughly to that of a helix having increasing diameter in the downstreamdirection (as known). Thus the centrifuging and the entrainment throughthe turning vanes numeral 12 a and 12 b and into the extraction manifoldfrom which particles are collected through the ducts numerals 16 a and16 b. The rotational systems on the chamber exhibited as numerals 14 cand 14 d shall additionally enable the centrifuge process to be enacted(with or without treads/threads—for example); as well as the engineshaft attached apparatus being major components.

The gaseous fluid or air shown as numeral 22 entering the engine throughthe inlet passes through the compressor numeral 24 where it iscompressed, and hence to the combustor numeral 26 where the air is mixedwith fuel and burned. The hot gases of combustion emerges at highvelocity from the combustor numeral 26 and passes sequentially throughthe high pressure turbine numeral 28 and low pressure turbine numeral 30where gases are expanded to extract energy there from. Energy extractedfrom the hot gases by turbine numeral 28 provides the driving force forthe compressor numeral 24 which is connected to turbine 28 by shaftnumeral 32 a. Energy extracted from the hot gases by turbine numeral 30provides the driving force for the main engine drive shaft numeral 32 bwhich delivers power to an energy using device, such as helicopter rotorsystem, (not exhibited). After exiting turbine numeral 30 the hot gasesof combustion passes through the engine exhaust duct numeral 34 whichincludes diffuser numeral 36 in which case gases are expanded and exitthe engine numeral 38. This is the formal function of numerous jetengines.

Ejector systems FIG. 6 numeral 40 includes control valve FIG. 6 numeral42 for controlling the amount of air bled from the compressor numeral 24thus flow of the fluid through the conduits numerals 20 a and 20 b toincrease efficiency of the gas turbine engine. When particle collectorseparation is not deemed necessary the ejector system may be used tointerrupt the flow of bled air. A modulating valve FIG. 6 numeral 44regulates the flow in the conduit thereby increasing engine efficiency.The guards/caps and/or screens as well as the rotational system shown inFIG. 1 numeral 10 a and 10 b as well as in FIG. 31 thru FIG. 56 (ofmetal/material) can be fastened inside the air inlet of the aircraft; aswell as fastened to the nacelle exterior portion; and/or in the airinlet extending out to the nacelle. This is also held true for FIG. 59the spherical and/or round structural support frame, with or withoutrotational system and/or treads/threads shown as serrated (for example).The support frame can take numerous forms such as illustrated in FIG. 57(rhombus) and FIG. 58 (parallelogram), for example. The guards/capsand/or screens can be fixed to the guards and/or guard frame and/or asseparate apparatus. Numeral 14 a and 14 b exhibits the rotationalsystems noted in rectangular form—this is one of the manipulations shownin FIG. 25. The rotational systems can be fixed to the guards cowlsand/or base or as a separate apparatus (of metal/material); thus therotational systems 14 a, 14 b, 14 c, and 14 d can be fixed/secured,adhered and/or attached to the nacelle/air inlet.

FIG. 1 numeral 46 a and 46 b (16 extensions/rods in each guards/capsand/or screen—for example)—can be separate apparatus—exhibitsextension(s)/rod(s) which can be fixed/secured, adhered, and/or attachedto the guard/cap and/or screens; as well as, can be fixed/secured,adhered and/or attached to the engine shaft apparatus and/or pole. Theseextensions/rods numeral 46 a and 46 b can extend from the inward and/oroutward portion of the guards/caps and/or screens; or from the screenslatitudinal vane(s) and fixed in the inward portion of the screen asexhibited (extensions/rods 46 a and 46 b can also be in multiples of2/numerous in numbers and/or odd numbers—of metal/material), arefixed/secured, positioned and/or adhered to numeral 48 a and 48 b, whichexhibits the treads/threads of the rotational systems allowing functionto occur. Extensions/Rods can also take a lacing configuration and/or alongitudinal configuration as well as having a curved aperture (forexample). Thus the treads/threads (for example) of the rotationalsystems production of various functions and movement allows gasseparation to occur—examples of movement and function is swift, pivot,clockwise (for example), time delayed, automated systems and/orhydraulics (for example—and/or for opening or closure of apparatus).Numeral 32 b exhibits the engine shaft extension(s) attachment and/orpole (of metal/material) thus adhered, fixed/secured and/or attached tothe guards/caps, screens and/or extensions. Numeral 32 a exhibits shaftfrom the high pressure turbine. Numeral 50 a, 50 b and 50 c thesecure/fixed, adhered, apparatus (of metal/material) attached to theengine and to the engine shaft extension(s) and/or pole-screens thatallows apparatus to be secure/fixed. Therefore, also allowing thecontinuous motion from the engine to occur without obstruction orfurther automation thereby inducing motion and creating the rotationand/or function for gas separation to occur without minimizing enginethrust a higher performance engine has been created. Since the particlesof matter are of small nature due to the guard(s)/cap(s) and/orscreen(s) in not allowing large matter to be ingested, particles mayalso remain in the collection chamber(s) which can be enclosed onceparticles enter from the duct(s), thereby offering an additionalsolution to this problem. The collection chamber 18 a, 18 b may includea mesh as discussed above. This is a prime solution not only fornumerous engines—jet, turboprop, turboshaft as well as for helicoptersand other VTOL/VSTOL aircraft. This is a prime solution for engines andpower plants and the like. Thus a guard(s)/cap(s) and/or screens alongwith the mechanism is significant. A casing may be added as deemed fitshown as numeral 52.

The following apparatus are various manipulations of the rotationalsystems (FIG. 23 thru FIG. 45—rotational systems and/or screens/guardsare of metal/material and can be in numerous forms—thus for example) canbe separate apparatus and/or secured/fixed, adhered and/or attached tothe cowls and/or base with or without treads/threads—as well as numerousmethods can be used other than treads/threads (for example). Variance inraised and or lowered in degrees of vanes, may also take a fly wheelcomposition FIG. 37 thru FIG. 43 allowing additional gas separation tooccur and turbine motion as well as used in guards (can be used withconicals/cones). The addition of a mesh FIGS. 46 a thru 46 d can be usedin FIG. 23 thru FIG. 45 and in other mechanisms. Devices may also bestationary for other engines and power plants and the like. All devicesare independent (and may also have a curved aperture—for example) andthus can be interchanged on all apparatuses.

FIG. 23 illustrates a rotational ring with serrated form (can also beinverted) shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 24 rotational ring with jagged form (can also be inverted) shown toadhere to the cowls and/or base, with and without treads/threads.

FIG. 25 rotational ring with rectangular form (can also be inverted)shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 26 rotational ring with jagged interlocked form (can also beinverted) shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 27 rotational ring with interlocked form (can also be inverted)shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 28 rotational ring as coiled form (can also be inverted withoutring but in ring formation—for example—as well as numerous coils) shownto adhere to the cowls and/or base, with or without treads/threads.

FIG. 29 rotational ring as slotted form (can also be inverted on theoutside as well as internal portion of the ring—for example as well asnumerous slots) shown to adhere to the cowls and/or base, with orwithout treads/threads.

FIG. 30 rotational ring as chain linked form (can also be invertedwithout ring but in ring formation—for example as well as numerouslinks) shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 31 rotational ring shown with screen—multiple in longitudinal andlatitudinal lines/form (can also be without ring but in ringformation—for example) shown to adhere to the cowls and/or base, with orwithout treads/threads.

FIG. 32 rotational ring shown with screen—multiple in latitudinallines/form (can also be without ring but in ring formation—for example)shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 33 rotational ring shown with screen-pierced form—multiple piercing(can also be without ring—for example—solid metal/material with piercedcube formation, can also be in other forms as well as geometric) shownto adhere to the cowls and/or base, with or without treads/threads.

FIG. 34 rotational ring shown with screen—multiple in longitudinallines/form (can also be without ring but in ring formation—for example)shown to adhere to the cowls and/or base, with or withouttreads/threads.

FIG. 35 rotational ring shown with screen—multiple in longitudinal andlatitudinal lines/form (thicker/bolder form, can also be without ringbut in ring formation—for example) shown to adhere to the cowls and/orbase, with or without treads/threads.

FIG. 36 rotational ring shown with screen—multiple in longitudinal andlatitudinal lines/form—pierced triangles (can also be without ring—forexample and can be in other forms as well as geometric) shown to adhereto the cowls and/or base, with or without treads/threads.

FIG. 37 rotational ring shown with screen and multiple vanes—screen inlongitudinal and latitudinal lines/form. Multiple vanes with screen(multiples of 2 and/or odd numbers). Apparatus can also be without ringbut in ring formation (for example).

FIG. 38 rotational ring shown with screen and multiple vanes—screen withmultiple vanes—screen in latitudinal lines/form. Multiple vanes withscreen (multiple of 2 and/or odd numbers). Apparatus can also be withoutring but in ring formation (for example).

FIG. 39 rotational ring shown with screen-pierced form and multiplevanes—multiple cube piercing. Multiple vanes with screen (multiples of 2and/or odd numbers). Apparatus can also be without ring but in ringformation—for example (solid metal/material with pierced formation, canalso be in other forms as well as geometric)—for example. FIG. 46 a thru46 d shown as the internal mesh for pierced mechanism; this mesh canalso be used in other mechanisms and/or manipulations.

FIG. 40 rotational ring shown with screen and multiple vanes—screen inlongitudinal lines/form. Multiple vanes with screen (multiples of 2and/or odd numbers). Apparatus can also be without ring but in ringformation (for example).

FIG. 41 rotational ring shown with screen and multiple vanes—screen inlongitudinal and latitudinal lines/form (thicker/bolder form). Multiplevanes with screen (multiples of 2 and/or odd numbers). Apparatus canalso be without ring but in ring formation (for example).

FIG. 42 rotational ring shown with screen and multiple vanes—screen inlongitudinal and latitudinal lines/form-pierced triangular form (can bein other forms as well as geometric). Multiple vanes with screen(multiples of 2 and/or odd numbers). Apparatus can also be without ringbut in ring formation (for example).

FIG. 43 rotational ring shown with screen and multiple vanes. Multiplesof vanes 2 and/or odd numbers. Apparatus can also be without ring but inring formation (for example).

FIG. 44 rotational shown with screen—screen in longitudinal andlatitudinal lines/form pierced triangular form (can be in other forms aswell as geometric compositions).

FIG. 45 rotational ring shown in cube form with height, width, anddepth—multiple cubes (can also be without ring but in ring formation—forexample—solid metal/material that may have cubes consisting of ainternal, side and/or bottom mesh in multiples of 2 and/or oddnumbers—for example. Note: cube can take other geometric forms.

FIG. 46 a, 46 b, 46 c and 46 d consists in variance in meshing:

-   -   (a) is latitudinal, variance in degree of aperture.    -   (b) is latitudinal and longitudinal and variance in degrees of        aperture (dense).    -   (c) is longitudinal variance in degree of aperture.    -   (d) is latitudinal and longitudinal variance in degrees of        aperture.

The following apparatus are various manipulations of the guards/capswith conical/cones (apparatus can be independent), shown with cowlsand/or base can be fixed/secured, adhered and/or attached; thus by beingfixed/secured, adhered, and/or attached to the rotational rings(apparatus can be separate) of FIG. 1 numerals 14 a and 14 b with orwithout treads/threads. Extensions/Rods FIG. 1 numerals 46 a and 46 b(apparatus can be independent and may have a curved aperture), can befixed/secured, adhered, positioned and/or attached to the guards/capsand/or screens; as well as to the engine shaft extension attachmentand/or pole, and/or rotational systems apparatus. All guard/cap nosescan be convex/concave, pointed and solid (for example) as well as othermanipulations listed (apparatus independently and/or whole can be ofmetal/material);

FIG. 47 the guard/cap shown as conical/cone, with multiple longitudinaland latitudinal lines/vanes form (rectangular-convex nose of the guard)shown to adhere to the cowls and/or base, as well as adhering to therotational rings numerals 14 a and 14 b with or without treads/threads;thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59respectively.

FIG. 48 the guard/cap shown as conical/cone, with multiple longitudinaland latitudinal lines/vanes form (convex nose of the guard with smallerscale of graduating metal/material or larger scale of metal/material—thenose of the guard/cap can be interchanged with other manipulations)shown to adhere to the cowls and/or base, as well as adhering to therotational rings numerals 14 a and 14 b with or without treads/threads;thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59respectively.

FIG. 49 the guard/cap shown as conical/cone, solid form (convex noseguard) shown to adhere to the cowls and/or base, as well as adhering tothe rotational rings numeral 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58,and 59 respectively.

FIG. 50 the guard/cap shown as conical/cone, with multiple longitudinallines/vanes form (convex nose guard) shown to adhere to the cowls and/orbase, as well as adhering to the rotational rings numeral 14 a and 14 bwith or without treads/threads; thus can be applied to FIG. 23 thruFIGS. 45, 57, 58 and 59 respectively. Not shown, although deemed fit isthe conical/cone, with multiple latitudinal lines/vanes form (convexnose guard) thus can adhere to the cowls and/or base, as well asadhering to the rotational rings numeral 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and59 respectively.

FIG. 51 the guard/cap shown as conical/cone, with multiple longitudinallines/vanes form (convex nose guard) shown to adhere to the cowls and/orbase, as well as adhering to the rotational rings numerals 14 a and 14 bwith or without treads/threads; thus can be applied to FIG. 23 thruFIGS. 45, 57, 58 and 59 respectively.

FIG. 52 the guard/cap shown as conical/cone, pierced triangularform—multiple in piercing (convex nose guard, can be various patterns ofpiercing) shown to adhere to the cowls and/or base, as well as adheringto the rotational rings numerals 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and59 respectively.

FIG. 53 the guard/cap shown as conical/cone, with multiple latitudinallines/vanes form (convex nose guard with nose guard and/or withcylindrical latitude form as conical/cone) shown to adhere to the cowlsand/or base, as well as adhering to the rotational rings numerals 14 aand 14 b with or without treads/threads; thus can be applied to FIG. 23thru FIGS. 45, 57, 58 and 59 respectively. Note, conical/cone may alsotake a latitudinal line/vanes.

FIG. 54 the guard/cap shown as conical/cone pierced triangularform—multiple piercing as well as longitudinal form (convex nose canalso be in other forms—with the addition of latitudinal lines/vanes mayoffer additional obstruction shown to adhere to the cowls and/or base,as well as adhering to the rotational rings numerals 14 a and 14 b withor without treads/threads; thus can be applied to FIG. 23 thru FIGS. 45,57 58 and 59 respectively.

FIG. 55 the guard/cap shown as conical/cone with multiple longitudinallines/vanes (convex nose guard) and centrifuge process on the exteriorof the conical/cone thus offering centrifuging process by turning vaneseach extending an arcuate distance of approximately 120 degrees, (forexample), shown to adhere to the cowls and/or base, as well as adheringto the rotational ring numerals 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and59 respectively. Note: conical/cone may also take a latitudinallines/vanes—not shown.

FIG. 56 the guard/cap shown as conical/cone with multiple longitudinallines/vanes (convex nose guard) with exterior of a series of turningvanes each extending an arcuate distance of approximately 120degrees—for example (degrees may vary depending on how may vanes areadded to the conical/cone); shown to adhere to the cowls and/or base, aswell as adhering to the rotational ring numerals 14 a and 14 b with orwithout treads/threads; thus can be applied to FIG. 23 thru FIGS. 45,57, 58 and 59 respectively. This conical is prime for deflectingshrapnel and thus returning shrapnel to the enemy without causingobstruction to engine components and yet offer maximization of gasseparation. Note; conical/cone may also take a latitudinallines/vanes—not shown.

The following device is the “Structural Support Frame System,” if fornumerous jets, turboprop, turboshaft, and other VTOL/VSTOL as well asengines and power plants and the like; with or without rotational systemas well as with or without treads/threads (for example). Rotationalsystem may be within the structural support frame and/or prior to thestructural support fame and/or henceforth after. Possible inclusion, ofthe guard(s)/cap(s) and/or screen(s) with the “Structural Support FrameSystem.”

FIG. 57 the structural support frame system shown in rhombus form withrectangular rotational system shown as FIG. 25, can be fixed/secured,adhered, and/or attached inside the air inlet of the aircraft, as wellas fastened to the nacelle exterior portion, and/or in the air inletextending out the nacelle (of metal/material).

FIG. 58 the structural support frame system shown in parallelogram formwith rectangular rotational system shown as FIG. 25 can befixed/secured, adhered, and/or attached inside the air inlet of theaircraft as well as fastened to the nacelle exterior portion, and/or inthe air inlet extending out the nacelle (of metal/material).

FIG. 59 the structural support frame system shown in spherical and/orround form with rectangular rotational system shown as FIG. 25 can befixed/secured, adhered, and/or attached inside the air inlet of theaircraft as well as fastened to the nacelle exterior portion, and/or inthe air inlet extending out to the nacelle (of metal/material).

The following apparatus are nose guards/caps shown in conical/cone formwith various interchanging nose guard/cap—may take the configuration ofconvex, concave and/or solid—for example. All nose guards areindependent and thus can be applicable and interchangeable on allconicals/cones. The following are manipulations of the conical/conesnose guards/caps;

FIG. 60. nose guard/cap shown as conical/cone form is solid formation(cone pointed). Such nose guard/cap can be solid in whole and/or partialand in kind.

FIG. 61. nose guard/cap shown as conical/cone form has multiplelongitudinal and latitudinal lines/vanes form (cone pointed). Such anose guard/cap can be solid in whole and/or partial and in kind.

FIG. 62 nose guard/cap shown as conical/cone form is solid formation(convex form). Such a nose guard/cap shown can be solid in whole and/orpartial and in kind.

FIG. 63 nose guard/cap shown as conical/cone form has multiplelongitudinal and latitudinal lines/vanes form (convex form). Such a noseguard/cap shown can be solid in whole and/or partial and in kind.

FIG. 64 nose guard/cap shown as conical/cone form is solid formation(rectangular form). Such a nose guard/cap shown can be solid in wholeand/or partial and in kind.

FIG. 65 nose guard/cap shown as conical/cone form has longitudinal andlatitudinal lines/vanes form (rectangular form). Such a nose guard/capshown can be solid in whole and/or partial and in kind.

FIG. 66 nose guard/cap shown as conical/cone form is solid formation(concave form). Such a nose guard/cap shown can be solid in whole and/orpartial and in kind.

FIG. 67 nose guard/cap shown conical/one form has longitudinal andlatitudinal lines/vanes form (concave form). Such a nose guard/cap canbe solid in whole and/or partial and in kind.

FIG. 2 illustrates an alternate embodiment exhibited in a isometricpartial view of apparatus and illustrates that the guards/caps and/orscreens (can be interchanged) is shown with longitudinal and latitudinalform. In FIG. 2 numeral 10 a the screens, can be fixed/secured, adhered,positioned and/or attached to the bases of the apparatus (can beseparate apparatus), and thus fastened. The centrifuge chamber/manifoldparticle collector exhibited by numerals 12 a and 12 b. The particleseparator exhibits a pair of spaced walls—within the conical/cone—forexample—(pierced screen shown as FIG. 33—can be internal part of themeshed screen(s) with vane(s)—for example—shown as FIG. 46 a thru 46 d)with rotational systems apparatus—exhibited by numerals 14 a with orwithout treads/threads—for example. Define as annular passageway therebetween, having at opposite ends thereof and outlet flow ofcommunication through two ducts exhibited by numerals 16 a and 16 blocated at opposite ends of the chamber. The vanes in the chamberexhibited by numeral 12 a and 12 b axially divide the chamber and definean annular extraction manifold within the conical/cone. The threeturning vanes each of which extends an arcuate distance of approximately120 degrees, (for example) it can be seen that no particle need travelmore than a circumferential distance of 120 degrees (for example) beforeentering the extraction manifold from which rebound into the engineinlet is reduced. Variances in degrees can occur with structuralconfiguration of guard(s)/cap(s) and/or screens(s). Number of collectorvanes may vary to meet the required amount for collector/separatorefficiency. The ducts are in direct communication with the collectionchambers exhibited by numerals 18 a and 18 b, and thus the collectionchamber is in direct communication with the two conduits exhibited bynumerals 20 a and 20 b. As air numeral 22, passes through the inletwhich is at a high velocity it is turned or centrifugedcircumferentially at such a downstream of the vanes, the air has bothangular and axial velocity. This is known as imparting “swirl” to thefluid stream. Small particles of foreign matter entrained in the airstream are also centrifuged, having small mass the particles are carriedalong with the swirling air. The particles with greater mass are not ofour concern due to the guard(s)/cap(s) and/or screen(s) are used forpreventive measure. A particle entrained in the air stream andcentrifuged will have both tangential and axial velocity downstream ofthe turning vanes. Both tangential and axial velocity in theory notsubjected to external forces travel in a straight line path to the outerperiphery of the passage way. In practice, the swirling air hassignificant effect on the particles trajectory which can be comparedroughly to that of a helix having increasing diameter in the downstreamdirection (as known). Thus the centrifuging and the entrainment throughthe turning vanes numeral 12 a and 12 b into the extraction manifoldfrom which particles are collected through the ducts numerals 16 a and16 b. The engine shaft attached apparatus numeral 32 b is thus beingmajor a component in allowing auto induced function for the rotationaland centrifuge process to occur within the conical/cone. The gaseousfluid or air shown as numeral 22 entering the engine through the inletpasses through the compressor numeral 24 where it is compressed, andhence to the combustor numeral 26 where the air is mixed with fuel andburned. The hot gases of combustion emerges at high velocity from thecombustor numeral 26 and passes sequentially through the high pressureturbine numeral 28 and low pressure turbine numeral 30 where gases areexpanded to extract energy there from. Energy extracted from the hotgases by turbine numeral 28 provides the driving force for thecompressor numeral 24 which is connected to turbine 28 by shaft numeral32 a. Energy extracted from the hot gases by turbine numeral 30 providesthe driving force for the main engine drive shaft numeral 32 b whichdelivers power to an energy using device, such as helicopter rotorsystem, (not exhibited). After exiting turbine numeral 30 the hot gasesof combustion passes through the engine exhaust duct numeral 34 whichincludes diffuser numeral 36 in which case gases are expanded and exitthe engine numeral 38. This is the formal function of numerous jetengines. Ejector systems FIG. 6 numeral 40 includes control valve FIG. 6numeral 42 for controlling the amount of air bled from the compressornumeral 24 thus flow of the fluid through the conduits numerals 20 a and20 b to increase efficiency of the gas turbine engine. When particlecollector separation is not deemed necessary the ejector system may beused to interrupt the flow of bled air. A modulating valve FIG. 6numeral 44 regulates the flow in the conduit thereby increasing engineefficiency. The guards/caps and/or screens as well as the rotationalsystem shown in FIG. 2 numeral 10 a as well as in FIG. 31 thru FIG. 56(of metal/material) can be fastened inside the air inlet of theaircraft; as well as fastened to the nacelle exterior portion; and/or inthe air inlet extending out to the nacelle. This is also held true forFIG. 59 the spherical and/or round structural support frame, with orwithout rotational system and/or treads/threads shown as serrated (forexample). The support frame can take numerous forms such as FIG. 57rhombus and FIG. 58 parallelogram (for example). The guards/caps and/orscreens can be fixed to the guards and/or guard frame and/or as separateapparatus. Numeral 14 a exhibits the rotational systems noted inrectangular form—this is one of the manipulations shown in FIG. 25. Therotational systems can be fixed to the guards cowls and/or base or as aseparate apparatus (of metal/material); thus to the rotational systems14 a, can be fixed/secured, adhered and/or attached to the nacelle/airinlet. FIG. 2 numeral 46 a (16 extensions/rods in the guards/caps and/orscreen—for example)—can be separate apparatus—exhibitsextension(s)/rod(s) which can be fixed/secured, adhered, and/or attachedto the guard/cap and/or screens; as well as, can be fixed/secured,adhered and/or attached to the engine shaft apparatus and/or poleapparatus. These extensions/rods numeral 46 a and 46 b can extend fromthe inward and/or outward portion of the guards/caps and/or screens; orfrom the screens latitudinal vane(s) and fixed in the inward portion ofthe screen as exhibited (extensions/rods 46 a can also be in multiplesof 2/numerous in numbers and/or odd numbers—of metal/material), arefixed/secured, positioned and/or adhered to numeral 48 a, which exhibitsthe treads/threads of the rotational systems allowing function to occur.Extensions/Rods can also take a lacing configuration and/or alongitudinal configuration as well as a curved aperture (for example).Thus inventing treads/threads (for example) of the rotational systemsproduction of various functions and movement shall therefore allow gasseparation to occur—examples of movement and function is swift, pivot,clockwise (for example), time delayed, automated systems and/orhydraulics (for example—and/or for opening or closure of apparatus).Numeral 32 b exhibits the engine shaft extension(s) attachment and/orpole (of metal/material) thus adhered, fixed/secured and/or attached tothe guards/caps, screens and/or extensions. Numeral 32 a exhibits shaftfrom the high pressure turbine. Numeral 50 a, the secure/fixed, adhered,apparatus (of metal/material) attached to the engine and to the engineshaft apparatus and/or pole-screens that allows apparatus to besecure/fixed. Therefore, also allowing the continuous motion from theengine to occur without obstruction or further automation therebyinducing motion and creating the rotation and/or function for gasseparation to occur without minimizing engine thrust we have created ahigher performance engine. Note: Since the particles of matter are ofsmall nature due to the guard(s)/cap(s) and/or screen(s) in not allowinglarge matter to be ingested, particles may also remain in the collectionchamber(s) which can be enclosed once particles enter from the duct(s),thereby offering an additional solution to this problem. This is a primesolution not only for numerous engines—jet, turboprop, turboshaft aswell as for helicopters and other VTOL/VSTOL aircraft. This is a primesolution for engines and power plants and the like. Thus aguard(s)/cap(s) and/or screens along with the mechanism is significant.A casing may be added as deemed fit shown as numeral 52. Alternatescreen/guards as illustrated in FIGS. 23-45 can also be incorporatedinto the embodiment illustrated in FIG. 2.

FIG. 3 shows an isometric partial expanded view of a multi vane doubleguards/caps and/or screens with engine attached apparatus and/or pole,with rotational systems. Centrifuge chamber/manifold particlecollector-separator shown with expanded view as well as multipleextensions/rods 46 a-18 for example, (exhibited in the inward positiontowards the security apparatus), exhibited in FIG. 2.

FIG. 4 shows an isometric partial view of a multi vane doubleguards/caps and/or screens with engine attached apparatus and/or pole,with rotational systems. Centrifuge chamber/manifold particlecollector-separator shown with expanded view as well as multipleextensions/rods 46 c—18 for example, (exhibited in the outwards positionof the security apparatus).

FIG. 5 shows a cross-sectional view of the separator exhibited in FIG. 1numerals 12 a and 12 b, as well as exhibited in FIG. 2 numerals 12 a and12 b. Thus the separator—three turning vanes each of which extends anacruate distance of approximately 120 degrees, (for example) it can beseen that no particle need travel more than a circumferential distanceof 120 degrees (for example) before entering the extraction manifoldfrom which rebound into the engine inlet is reduced. Variances indegrees can occur with structural configuration of guard(s)/cap(s)and/or screen(s), we note that separators turning vanes in FIG. 1 andFIG. 2 are exhibited on the conical/cone (for example).

FIG. 6 shows ejector systems numeral 40 includes the control valvenumeral 42 for controlling the amount of air bled from the compressorFIG. 1 and FIG. 2 numeral 24 thus flow of the fluid through the conduitsFIG. 1 and FIG. 2 numerals 20 a and 20 b to increase efficiency of thegas turbine engine. When particle collector separation is not deemednecessary the ejector system may be used to interrupt the flow of bledair. A modulating valve exhibited in FIG. 6 numeral 44 regulates theflow in the conduit thereby increasing engine efficiency.

FIG. 7 shows the manifold sectional; thereby attached to the engineapparatus and/or pole—(apparatus can be single, or attached,fixed/secured on the engine attached apparatus and/or pole, orfixed/secured on the guard(s)/cap(s) and/or screen(s).

FIG. 8 illustrates another alternate embodiment of Single/MultipleGuard(s)/Cap(s) and/or Screen(s) with Engine Systems Attached Apparatusand/or Pole with Rotational System(s); exhibited in a isometric partialview of apparatus and noted that the guards/caps and/or screens (can beinterchanged) is shown with longitudinal and latitudinal form. In FIG. 8numeral 58 exhibits conical/cone with convex nose guard (conicals/conesmay be suited for example are FIG. 47 thru FIG. 56 as well FIG. 10numeral 60 the darted conical/cone) exhibiting cowl and/or base asnumeral 56 thereby attached to the rotational systems noted inrectangular form exhibited as numerals 14 a and 14 b—this is one of themanipulations shown in FIG. 25. The rotational systems can be fixed tothe guards cowl and/or base or as separate apparatus (ofmetal/material); thus the rotational systems 14 a and 14 b can befixed/secured, adhered and/or attached to the nacelle/air inlet. FIG. 8numerals 46 a and 46 b (exhibits extensions/rods—46 a—10extensions/rods, 46 b 12 extensions/rods for example) can be separateapparatus—exhibits extension(s)/rod(s) which can be fixed/secured,adhered, and/or attached to the guard/cap and or screens; as well asfixed/secured, adhered and/or attached to the engine shaft extension(s)and/or pole apparatus. These extensions/rods numerals 46 a and 46 b canextend from the inward and/or outward portion of the guards/caps and/orscreens; or from the screen latitudinal vane(s)—(if screen is added) andfixed/secured, attached and/or adhered to the inward portion of theguards/caps and/or screens. Extensions/Rods 46 a and 46 b can also be inmultiples of 2/numerous in numbers and or odd numbers, extensions/rodsmay have a curved aperture for greater gas separation—of metal/material.Conicals/cones with multi vanes have a greater degree of gas separationthereby engine to function more efficiently.

As air numeral 22, passes through the inlet which is at a high velocityit is turned at such a downstream by the vanes, the air has both angularand axial velocity. This is known as imparting “swirl” to the fluidstream. Small particles of foreign matter entrained in the air streamare carried along with the swirling air. The particles with greater massare not of our concern due to the guard(s)/cap(s) and/or screen(s) areused for preventive measure. A particle entrained in the air stream willhave both tangential and axial velocity downstream of the turning vanes.Both tangential and axial velocity in theory are not subjected toexternal forces travel in a straight line path to the outer periphery ofthe passage way. In practice, the swirling air has significant effect onthe particles trajectory which can be compared roughly to that of ahelix having increasing diameter in the downstream direction (as known).The rotational systems numerals 14 a and 14 b with or withouttreads/threads numerals 48 a and 48 b shall enable gas separation totake place as well as guard from foreign objects. The gaseous fluid orair shown as numeral 22 entering the engine through the inlet passesthrough the compressor numeral 24 where it is compressed, and hence tothe combustor numeral 26 where the air is mixed with fuel and burned.The hot gases of combustion emerges at high velocity from the combustornumeral 26 and passes sequentially through the high pressure turbinenumeral 28 and low pressure turbine numeral 30 where gases are expandedto extract energy there from. Energy extracted from the hot gases byturbine numeral 28 provides the driving force for the compressor numeral24 which is connected to turbine 28 by shaft numeral 32 a. Energyextracted from the hot gases by turbine numeral 30 provides the drivingforce for the main engine drive shaft numeral 32 b which delivers powerto an energy using device, such as helicopter rotor system, (notexhibited). After exiting turbine numeral 30 the hot gases of combustionpasses through the engine exhaust duct numeral 34 which includesdiffuser numeral 36 in which case gases are expanded and exit the enginenumeral 38. This is the formal function of numerous jet engines. Ejectorsystems as well as conduits may also be added (not exhibited in FIG. 8but exhibited in FIG. 1 and FIG. 2) FIG. 6 numeral 40 includes controlvalve FIG. 6 numeral 42 for controlling the amount of air bled from thecompressor numeral 24 thus flow of the fluid through the conduits meansnumerals 20 a and 20 b to increase efficiency of the gas turbine engine.A modulating valve FIG. 6 numeral 44 regulates the flow in the conduitthereby increasing engine efficiency. The guards/caps and/or screens aswell as the rotational system 14 a and 14 b shown in FIG. 8 numeral 58are also deemed appropriate use and possible to be used in FIG. 31 thruFIG. 56 for example (of metal/material) thus can be fastened inside theair inlet of the aircraft; as well as fastened to the nacelle exteriorportion; and/or in the air inlet extending out to the nacelle. This isalso held true for FIG. 59 the spherical and/or round structural supportframe, with or without rotational system and/or treads/threads shown asserrated (for example). We note support frame can take numerous formssuch as FIG. 57 rhombus and FIG. 58 parallelogram (for example). Theguards/caps and/or screens can be fixed to the guards and/or guard frameand/or as separate apparatus. Thus inventing the treads/threads (forexample) of the rotational systems production of various functions andmovement shall therefore allow gas separation to occur—examples ofmovement and function is swift, pivot, clockwise (for example), timedelayed, automated systems and/or hydraulics (for example—and/or foropening or closure of apparatus). Numeral 32 b exhibits the engine shaftextension(s) attachment and/or pole (of metal/material) thus adhered,fixed/secured and/or attached to the guards/caps, screens and/orextensions. Numeral 32 a exhibits shaft from the high pressure turbine.Numeral 50 a, 50 b and 50 c the secure/fixed, adhered, apparatus (ofmetal/material) attached to the engine and to the engine shaftextension(s) and/or pole-screens that allows apparatus to besecure/fixed. Therefore, also allowing the continues motion from theengine to occur without obstruction or further automation therebyinducing motion and creating the rotation and/or function for gasseparation to occur without minimizing engine thrust we have created ahigher performance engine. Note: Since the particles of matter are ofsmall nature due to the guard(s)/cap(s) and/or screen(s) in not allowinglarge matter to be ingested, particles may also remain in the collectionchamber(s) (not exhibited in FIG. 8 but shown in FIG. 1 and FIG. 2numerals 18 a and 18 b) but which can be enclosed once particles enterfrom the duct(s), thereby offering an additional solution to thisproblem. This is a prime solution not only for numerous engines—jet,turboprop, turboshaft as well as for helicopters and other VTOL/VSTOLaircraft. This is a prime solution for engines and power plants and thelike. Thus a guard(s)/cap(s) and/or screens along with the mechanism issignificant. A casing may be added as deemed fit shown in FIG. 1 andFIG. 3 numeral 52.

FIG. 9 shows an isometric partial expanded view of a double guards/capsand/or screens with the engine attached apparatus and/or pole, withrotational system.

The following apparatus are various manipulations of the rotationalsystems (FIG. 23 thru FIG. 45—rotational systems and/or screens/guardsare of metal/material and can be in numerous forms—thus for example) canbe separate apparatus and/or secured/fixed, adhered and/or attached tothe cowls and/or base with or without treads/threads—as well as numerousmethods can be used other than treads/threads (for example). Variance inraised and or lowered in degrees of vanes, may also take a fly wheelcomposition FIG. 37 thru FIG. 43 allowing additional gas separation tooccur and turbine motion as well as used in guards (can be used withconicals/cones). The addition of a mesh 46 a thru 46 d can be used inFIG. 23 thru FIG. 45 and in other mechanisms. Devices may also bestationary for other engines and power plants and the like. All devicesare independent (and may also have a curved aperture—for example) andthus can be interchanged on all apparatuses. Alternate screen/guards asdiscussed above and illustrated in FIGS. 23-45 can also be incorporatedinto the embodiment illustrated in FIG. 3.

FIG. 10 represents another alternate embodiment of Single/MultipleGuard(s)/Cap(s) and/or Screen(s) with Engine Systems RetractableAttached Apparatus and/or Pole with Rotational System(s) exhibited in aisometric partial view of apparatus and noted that the guards/capsand/or screens (can be interchanged) is shown with longitudinal andlatitudinal form. In FIG. 10 numeral 60 exhibits the darted conical/conewith convex nose guard, (conicals/cones may be suited for example areFIG. 47 thru FIG. 56) exhibiting cowl and/or base as numeral 56 and aplurality of spokes 46 a, 46 b, pivotally attached on one end to thebase 56 forming a cone shape in one position where the spokes 46 a, 46 bgenerally divergent on one end as shown, for example, in FIG. 10 and aone or more intermediate positions, for example, as shown in FIGS. 12-14wherein the angle between the spokes 46 a, 46 b and the shaft 32 b isvaried from that shown in FIG. 10. The base 56 may be attached to therotational systems noted in rectangular form exhibited as numerals 14 aand 14 b—this is one of the manipulations shown in FIG. 25. Therotational systems can be fixed to the guards cowl and/or base or asseparate apparatus (of metal/material); thus the rotational systems 14 aand 14 b can be fixed/secured, adhered and/or attached to thenacelle/air inlet. FIG. 10 numerals 46 a and 46 b (exhibitsextensions/rods—46 a—10 extensions/rods, 46 b 12 extensions/rods forexample) can be separate apparatus—exhibits extension(s)/rod(s) whichcan be fixed/secured, adhered, and/or attached to the guard/cap and orscreens; as well as fixed/secured, adhered and/or attached to the engineshaft extension(s) and/or pole apparatus. These extensions/rods numerals46 a and 46 b can extend from the inward and/or outward portion of theguards/caps and/or screens; or from the screen latitudinal vane(s), (ifscreen is added) and fixed/secured, attached and/or adhered to theinward portion of the guards/caps and/or screens. Extensions/Rods 46 aand 46 b can also be in multiples of 2/numerous in numbers and or oddnumbers, extensions/rods may have a curved aperture for greater gasseparation—of metal/material. Conicals/cones with multi vanes have agreater degree of gas separation thereby engine to function moreefficiently. As air numeral 22, passes through the inlet which is at ahigh velocity it is turned at such a downstream by the vanes, the airhas both angular and axial velocity. This is known as imparting “swirl”to the fluid stream. Small particles of foreign matter entrained in theair stream are carried along with the swirling air. The particles withgreater mass are not of our concern due to the guard(s)/cap(s) and/orscreen(s) are used for preventive measure. A particle entrained in theair stream will have both tangential and axial velocity downstream ofthe turning vanes. Both tangential and axial velocity in theory are notsubjected to external forces travel in a straight line path to the outerperiphery of the passage way. In practice, the swirling air hassignificant effect on the particles trajectory which can be comparedroughly to that of a helix having increasing diameter in the downstreamdirection (as known). The rotational systems numerals 14 a and 14 b withor without treads/threads numerals 48 a and 48 b shall enable gasseparation to take place as well as guard from foreign objects. Thegaseous fluid or air shown as numeral 22 entering the engine through theinlet passes through the compressor numeral 24 where it is compressed,and hence to the combustor numeral 26 where the air is mixed with fueland burned. The hot gases of combustion emerges at high velocity fromthe combustor numeral 26 and passes sequentially through the highpressure turbine numeral 28 and low pressure turbine numeral 30 wheregases are expanded to extract energy there from. Energy extracted fromthe hot gases by turbine numeral 28 provides the driving force for thecompressor numeral 24 which is connected to turbine 28 by shaft numeral32 a. Energy extracted from the hot gases by turbine numeral 30 providesthe driving force for the main engine drive shaft numeral 32 b whichdelivers power to an energy using device, such as helicopter rotorsystem, (not exhibited). After exiting turbine numeral 30 the hot gasesof combustion passes through the engine exhaust duct numeral 34 whichincludes diffuser numeral 36 in which case gases are expanded and exitthe engine numeral 38. This is the formal function of numerous jetengines. Ejector systems and centrifuge vanes may also be added thus aswell as the conduits if deemed to (not exhibited in FIG. 10 butexhibited in FIG. 1 and FIG. 2) FIG. 6 numeral 40 includes control valveFIG. 6 numeral 42 for controlling the amount of air bled from thecompressor numeral 24 thus flow of the fluid through the conduits meansnumerals 20 a and 20 b to increase efficiency of the gas turbine engine.A modulating valve FIG. 6 numeral 44 regulates the flow in the conduitthereby increasing engine efficiency. The guards/caps and/or screens aswell as the rotational system 14 a and 14 b shown in FIG. 10 numeral 60(darted guard) are also deemed appropriate use and possible to be usedin FIG. 31 thru FIG. 56 for example (of metal/material) thus can befastened inside the air inlet of the aircraft; as well as fastened tothe nacelle exterior portion; and/or in the air inlet extending out tothe nacelle. This is also held true for FIG. 59 the spherical and/orround structural support frame, with or without rotational system and/ortreads/threads shown as serrated (for example). We note support framecan take numerous forms such as FIG. 57 rhombus and FIG. 58parallelogram (for example). The guards/caps and/or screens can be fixedto the guards and/or guard frame and/or as separate apparatus. Thusinventing the treads/threads (for example) of the rotational systemsproduction of various functions and movement shall therefore allow gasseparation to occur—examples of movement and function is swift, pivot,clockwise (for example), time delayed, automated systems and/orhydraulics (for example—and/or for opening or closure of apparatus).Numeral 32 b exhibits the engine shaft extension(s) attachment and/orpole (of metal/material) thus adhered, fixed/secured and/or attached tothe guards/caps, screens and/or extensions. Numeral 32 a exhibits shaftfrom the high pressure turbine. Numeral 50 a, 50 b and 50 c thesecure/fixed, adhered, apparatus (of metal/material) attached to theengine and to the engine shaft extension(s) and/or pole-screens thatallows apparatus to be secure/fixed. Therefore, also allowing thecontinuous motion from the engine to occur without obstruction orfurther automation thereby inducing motion and creating the rotationand/or function for gas separation to occur without minimizing enginethrust we have created a higher performance engine. Note: Since theparticles of matter are of small nature due to the guard(s)/cap(s)and/or screen(s) in not allowing large matter to be ingested, particlesmay also remain in the collection chamber(s) (not exhibited in FIG. 10but shown in FIG. 1 numerals 18 a and 18 b and FIG. 2 numerals 18 a and18 b) but which can be enclosed once particles enter from the duct(s),thereby offering an additional solution to this problem. Formalretraction process shall commence by the conical/cone thus withdispersing movement (shown in FIGS. 12, 13 and 14) by center axis inmultiples of 2 in numbers and/or odd numbers thus retract over the inletand thus allow the extensions/rods to commence into a folding and/or arelaced pattern for example as thus the conical/cone may also be deemedinto a folding or laced pattern (shown by isometric partial expandedview FIG. 11) which shall be taken into account by the type of inlet ofa particular aircraft as well as the type of engine. This can also be asignificant process for other engines and power plants and the like.FIG. 10 numerals 62 a and 62 b exhibit the retraction slots in whichcase for example the use hydraulics/automation process shall commence.The retraction apparatus exhibited as FIG. 10 numerals 64 a, 64 b, and64 c shall allow the attached apparatus and/or pole to be condensedwithin the pole in a stacking manner or on the exterior portion of thepole in a stacking matter—for example—FIG. 18 and FIG. 19 exhibit aexpanded view of retractors (this shall very on the type of aircraftand/or engine). If centrifuge chamber manifold particle collector isdeemed fit to use thus variance on the type of aircraft and/or engine aswell as power plants and the like—similar process shall commence therebya folding and/or laced pattern—for example. Prior works exhibitaircraft—conicals/cones used for directional purposes by means ofhydraulic movement thus back and forth although a lack of efficiency andenergy has not allowed these types of aircraft to attain the highestperformance deemed possible, by the use of the rotational system(s) andbeing cost effective and efficient we attain a higher degree ofperformance that allows gas separation to take place as well asmaintaining and not compromising the engine thrust. The multi vaneconical—for example offers a greater degree of gas separation than asolid conical. Variance in guards/caps and/or screens vanes and/or meshoffer variances in degrees of gas separation. Thus, the three centrifugemulti vane conical/cone exhibited as FIG. 55 exhibits offers centrifugeprocess on the external means of conical thereby offering as well asdirection this is also deemed similar in nature with FIG. 56 the multivane centrifuge deflector conical/cone offers gas separation,directional purposes as well as deflecting shrapnel from enemies attack.This is a prime solution not only for numerous engines—jet, turboprop,turboshaft as well as for helicopters and other VTOL/VSTOL aircraft.This is a prime solution as well as for engines and power plants and thelike. Thus a guard(s)/cap(s) and/or screens along with the mechanism issignificant. A casing may be added as deemed fit shown in FIG. 1 andFIG. 3 numeral 52.

FIG. 9 shows an isometric partial expanded view of a doubleguards/caps/and/or screens with the engine attached apparatus and/orpole, with rotational system. In addition, alternate screen/guards asdiscussed above can be incorporated into the embodiment illustrated inFIG. 10.

The following apparatus are various manipulations of the guards/capswith conical/cones (apparatus can be independent), shown with cowlsand/or base can be fixed/secured, adhered and/or attached; thus by beingfixed/secured, adhered, and/or attached to the rotational rings(apparatus can be separate) of FIG. 1 numerals 14 a and 14 b with orwithout treads/threads. Extensions/Rods FIG. 1 numerals 46 a and 46 b(apparatus can be independent and may have a curved aperture), can befixed/secured, adhered, positioned and/or attached to the guards/capsand/or screens; as well as to the engine shaft extension attachmentand/or pole, and/or rotational systems apparatus. All guard/cap nosescan be convex/concave, pointed and solid (for example) as well as othermanipulations listed (apparatus independently and/or whole can be ofmetal/material):

FIG. 47 the guard/cap shown as conical/cone, with multiple longitudinaland latitudinal lines/vanes form (rectangular-convex nose of the guard)shown to adhere to the cowls and/or base, as well as adhering to therotational rings numerals 14 a and 14 b with or without treads/threads;thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59respectively.

FIG. 48 the guard/cap shown as conical/cone, with multiple longitudinaland latitudinal lines/vanes form (convex nose of the guard with smallerscale of graduating metal/material or larger scale of metal/material—thenose of the guard/cap can be interchanged with other manipulations)shown to adhere to the cowls and/or base, as well as adhering to therotational rings numerals 14 a and 14 b with or without treads/threads;thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and 59respectively.

FIG. 49 the guard/cap shown as conical/cone, solid form (convex noseguard) shown to adhere to the cowls and/or base, as well as adhering tothe rotational rings numeral 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58,and 59 respectively.

FIG. 50 the guard/cap shown as conical/cone, with multiple longitudinallines/vanes form (convex nose guard) shown to adhere to the cowls and/orbase, as well as adhering to the rotational rings numeral 14 a and 14 bwith or without treads/threads; thus can be applied to FIG. 23 thruFIGS. 45, 57, 58 and 59 respectively. Not shown, although deemed fit isthe conical/cone, with multiple latitudinal lines/vanes form (convexnose guard) thus can adhere to the cowls and/or base, as well asadhering to the rotational rings numeral 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and59 respectively.

FIG. 51 the guard/cap shown as conical/cone, with multiple longitudinallines/vanes form (convex nose guard) shown to adhere to the cowls and/orbase, as well as adhering to the rotational rings numerals 14 a and 14 bwith or without treads/threads; thus can be applied to FIG. 23 thruFIGS. 45, 57, 58 and 59 respectively.

FIG. 52 the guard/cap shown as conical/cone, pierced triangularform—multiple in piercing (convex nose guard, can be various patterns ofpiercing) shown to adhere to the cowls and/or base, as well as adheringto the rotational rings numerals 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and59 respectively.

FIG. 53 the guard/cap shown as conical/cone, with multiple latitudinallines/vanes form (convex nose guard with nose guard and/or withcylindrical latitude form as conical/cone) shown to adhere to the cowlsand/or base, as well as adhering to the rotational rings numerals 14 aand 14 b with or without treads/threads; thus can be applied to FIG. 23thru FIGS. 45, 57, 58 and 59 respectively. Note, the conical/cone mayalso take a latitudinal lines/vanes.

FIG. 54 the guard/cap shown as conical/cone pierced triangularform—multiple piercing as well as longitudinal form (convex nose canalso be in other forms—with the addition of latitudinal lines/vanes mayoffer additional obstruction shown to adhere to the cowls and/or base,as well as adhering to the rotational rings numerals 14 a and 14 b withor without treads/threads; thus can be applied to FIG. 23 thru FIGS. 45,57 58 and 59 respectively.

FIG. 55 the guard/cap shown as conical/cone with multiple longitudinallines/vanes (convex nose guard) and centrifuge process on the exteriorof the conical/cone thus offering centrifuging process by turning vaneseach extending an arcuate distance of approximately 120 degrees, (forexample), shown to adhere to the cowls and/or base, as well as adheringto the rotational ring numerals 14 a and 14 b with or withouttreads/threads; thus can be applied to FIG. 23 thru FIGS. 45, 57, 58 and59 respectively. Note: conical/cone may also take a latitudinallines/vanes—not shown.

FIG. 56 the guard/cap shown as conical/cone with multiple longitudinallines/vanes (convex nose guard) with exterior of a series of turningvanes each extending an arcuate distance of approximately 120degrees—for example (degrees may vary depending on how may vanes areadded to the conical/cone); shown to adhere to the cowls and/or base, aswell as adhering to the rotational ring numerals 14 a and 14 b with orwithout treads/threads; thus can be applied to FIG. 23 thru FIGS. 45,57, 58 and 59 respectively. This conical is prime for deflectingshrapnel and thus returning shrapnel to the enemy without causingobstruction to engine components and yet offer maximization of gasseparation. Note; conical/cone may also take a latitudinallines/vanes—not shown.

The following device is the “Structural Support Frame System,” if fornumerous jets, turboprop, turboshaft, and other VTOL/VSTOL as well asengines and power plants and the like; with or without rotational systemas well as with or without treads/threads (for example). Rotationalsystem may be within the structural support frame and/or prior to thestructural support fame and/or henceforth after. Possible inclusion, ofthe guard(s)/cap(s) and/or screen(s) with the “Structural Support FrameSystem.”

FIG. 57 the structural support frame system shown in rhombus form withrectangular rotational system shown as FIG. 25, can be fixed/secured,adhered, and/or attached inside the air inlet of the aircraft, as wellas fastened to the nacelle exterior portion, and/or in the air inletextending out the nacelle (of metal/material).

FIG. 58 the structural support frame system shown in parallelogram formwith rectangular rotational system shown as FIG. 25 can befixed/secured, adhered, and/or attached inside the air inlet of theaircraft as well as fastened to the nacelle exterior portion, and/or inthe air inlet extending out the nacelle (of metal/material).

FIG. 59 the structural support frame system shown in spherical and/orround form with rectangular rotational system shown as FIG. 25 can befixed/secured, adhered, and/or attached inside the air inlet of theaircraft as well as fastened to the nacelle exterior portion, and/or inthe air inlet extending out to the nacelle (of metal/material).

The following apparatus are nose guards/caps shown in conical/cone formwith various interchanging nose guard/cap—may take the configuration ofconvex, concave and/or solid—for example. All nose guards areindependent and thus can be applicable and interchangeable on allconicals/cones. The following are manipulations of the conical/conesnose guards/caps:

FIG. 60, nose guard/cap shown as conical/cone form is solid formation(cone pointed). Such nose guard/cap can be solid in whole and/or partialand in kind.

FIG. 61, nose guard/cap shown as conical/cone form has multiplelongitudinal and latitudinal lines/vanes form (cone pointed). Such anose guard/cap can be solid in whole and/or partial and in kind.

FIG. 62 nose guard/cap shown as conical/cone form is solid formation(convex form). Such a nose guard/cap shown can be solid in whole and/orpartial and in kind.

FIG. 63 nose guard/cap shown as conical/cone form has multiplelongitudinal and latitudinal lines/vanes form (convex form). Such a noseguard/cap shown can be solid in whole and/or partial and in kind.

FIG. 64 nose guard/cap shown as conical/cone form is solid formation(rectangular form). Such a nose guard/cap shown can be solid in wholeand/or partial and in kind.

FIG. 65 nose guard/cap shown as conical/cone form has longitudinal andlatitudinal lines/vanes form (rectangular form). Such a nose guard/capshown can be solid in whole and/or partial and in kind.

FIG. 66 nose guard/cap shown as conical/cone form is solid formation(concave form). Such a nose guard/cap shown can be solid in whole and/orpartial and in kind.

FIG. 67 nose guard/cap shown conical/one form has longitudinal andlatitudinal lines/vanes form (concave form). Such a nose guard/cap canbe solid in whole and/or partial and in kind.

FIG. 11 shows an isometric partial expanded view of the doubleguards/caps and/or screen with the engine attached apparatus and/orpole, with rotational systems. The formal process and thus descriptionof is noted in FIG. 10 although in FIG. 11 we note the solid partialview conical as numeral 58.

FIG. 12 shows dispersing of a conical exhibited in numeral 66 and thusexhibiting cowl numeral 56 for retraction process; conical may take amultiple forms for example FIG. 47 thru FIG. 56. Dispersing for examplemay be in multiples of 2 in numbers and/or odd numbers—ofmetal/material.

FIG. 13 shows dispersing of a conical exhibited in numeral 66 and thusexhibiting cowl numeral 56 for retraction process; conical may take amultiple forms for example FIG. 47 thru FIG. 56. Dispersing for examplemay be in multiples of 2 in numbers and/or odd numbers—ofmetal/material. Exhibiting also 54 a the additional multi vane conical;as dispersing occurs the multi vane conical is exhibited to theforefront by hydraulic/automated means to maintain the integrity of theengine components as dispersing occurs.

FIG. 14 shows dispersing of a conical exhibited in numeral 66 and thusexhibiting cowl numeral 56 for retraction process; conical may take amultiple forms for example FIG. 47 thru FIG. 56. Dispersing for examplemay be in multiples of 2 in numbers and/or odd numbers—ofmetal/material. Exhibiting also 54 b the additional multi vane conicalwith spherical vanes; as dispersing occurs the multi vane conical isexhibited to the forefront by hydraulic/automated means to maintain theintegrity of the engine components as dispersing occurs.

FIG. 15 shows the engine shaft extension security attachment and/orpole, diamond form (for example). This device shall allow security to bemaintained without obstruction of function by the rotational system(s).

FIG. 16 shows the engine shaft extension security attachment and/orpole, cylindrical form (for example). This device shall allow securityto be maintained without obstruction of function by the rotationalsystem(s).

FIG. 17 shows the engine shaft extension security attachment and/orpole, in rectangular form (for example). The device shall allow securityto be maintained without obstruction of function by the rotationalsystem(s).

FIG. 18 shows the multiple section engine attachment for retractionprocess of the apparatus and/or pole, this device may be used in FIG.10. Not exhibited although deemed fit is the multi-laced engineattachment apparatus and/or pole may also have retracting properties orwithout (for example).

FIG. 19 shows multiple section engine attachment for retraction processof the apparatus and/or pole, exhibited in FIG. 10 numerals 64 a, 64 b,and 64 c.

FIG. 20 shows longitudinal apparatus and/or pole for numerous dualinlets, with dual extending apparatus from the pole for the inlet—thusshall function similar to engine shaft attached apparatus and/or polealthough for a dual inlet. This device may also be used for otherengines and power plants and the like.

FIG. 21 shows longitudinal engine attached apparatus and/or pole forinlet, this device may also be used for other engines and power plantsand the like.

FIG. 22 shows longitudinal attached apparatus and/or pole for numerousdual inlet, with dual extending apparatus for both/opposite side of thepole for the inlet, this device may also be use for other engines andpower plants and the like.

Obviously, many modifications and variations of the present inventionare possible in light of the above teachings. Thus, it is to beunderstood that, within the scope of the appended claims, the inventionmay be practiced otherwise than as specifically described above.

1. An air intake guard system for a turbine having a housing for use inan air intake cavity comprising: one or more guards in communicationwith an engine shaft extension configured to be in communication withsaid air intake cavity in said housing; a centrifuge chamber; one ormore rotating vanes mounted for rotational movement in said centrifugechamber, said vanes configured to conform to a predetermined shape ofsaid air intake cavity; a passageway in communication with saidcentrifuge chamber for collecting foreign particles in said centrifugechamber, said passageway formed as part of said housing and extendingaxially along said housing; and an outlet chamber in communication withsaid centrifuge chamber for discharging said foreign particles outsideof said housing.
 2. The system as recited in claim 1, wherein saidpredetermined shape is cylindrical.
 3. The system as recited in claim 2,wherein said system includes two guards.
 4. The system as recited inclaim 3, wherein said two guards are spaced apart and define saidcentrifuge chamber therebetween.
 5. The system as recited in claim 1,wherein said predetermined shape is conical.
 6. The system as recited inclaim 1, wherein said one or more guards are retractable.
 7. The systemas recited in claim 1, wherein said one or more rotating vanes areconfigured to be retractable.
 8. The system as recited in claim 1,wherein said predetermined shape is rectangular.
 9. An air intake guardsystem for a turbine having a housing for use in an air intake cavitycomprising: two or more guards configured to be in communication withsaid air intake cavity in said housing; a centrifuge chamber; one ormore rotating vanes mounted for rotational movement in said centrifugechamber, said vanes configured to conform to a predetermined shape ofsaid air intake cavity; a passageway in communication with saidcentrifuge chamber for collecting foreign particles in said centrifugechamber, said passageway formed as part of said housing and extendingaxially along said housing; and, an outlet chamber in communication withsaid certrifuge chamber for discharging said foreign particles outsideof said housing.
 10. An air intake guard system for a turbine having ahousing for use in an air intake cavity comprising: one or more guardsconfigured to be in communication with said air intake cavity in saidhousing; a centrifuge chamber; one or more rotating vanes mounted forrotational movement in said centrifuge chamber, said vanes configured toconform to a predetermined shape of said air intake cavity wherein thepredetermined shape is at least one from the group comprising conicaland rectangular; a passageway in communication with said centrifugechamber for collecting foreign particles in said centrifuge chamber,said passageway formed as part of said housing and extending axiallyalong said housing; and an outlet chamber in communication with saidcertrifuge chamber for discharging said foreign particles outside ofsaid housing.
 11. An air intake guard system for a turbine having ahousing for use in an air intake cavity comprising: one or moreretractable guards configured to be in communication with said airintake cavity in said housing; a centrifuge chamber; one or morerotating vanes mounted for rotational movement in said centrifugechamber, said vanes configured to conform to a predetermined shape ofsaid air intake cavity; a passageway in communication with saidcentrifuge chamber for collecting foreign particles in said centrifugechamber, said passageway formed as part of said housing and extendingaxially along said housing; and an outlet chamber in communication withsaid certrifuge chamber for discharging said foreign particles outsideof said housing.